An Experimental Evaluation of the Performance Deficit of an Aircraft Engine Starter Turbine 801137
An experimental investigation was made at NASA-Lewis Research Center to determine the reasons for the low aerodynamic performance of a 13.5-centimeter-tip-diameter aircraft engine starter turbine. The investigation consisted of an evaluation of both the stator and the stage. An approximate ten percent improvement in turbine efficiency was obtained when the honeycomb shroud over the rotor blade tips was filled to obtain a solid shroud surface.
Citation: Haas, J., Roelke, R., and Hermann, P., "An Experimental Evaluation of the Performance Deficit of an Aircraft Engine Starter Turbine," SAE Technical Paper 801137, 1980, https://doi.org/10.4271/801137. Download Citation
Author(s):
Jeffrey E. Haas, Richard J. Roelke, Paul Hermann
Pages: 12
Event:
Aerospace Congress and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Aircraft
Starters and starting
Aerodynamics
Propellers and rotors
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